Methods for Forming a Composite Blade Stiffener and Facilitating Application of Barely Visible Impact Damage Treatments

ABSTRACT

An example method for forming a flat composite charge into a composite blade stiffener includes cutting a flat composite charge along a cut line into a first piece and a second piece having an angle, positioning the first piece and the second piece of the flat composite charge on a forming mandrel about a tooling plunger, activating the tooling plunger to drive the first piece and the second piece into a cavity of the forming mandrel resulting in the first piece and the second piece folding at the cut line, withdrawing the tooling plunger from the cavity of the forming mandrel, compressing the forming mandrel to apply a lateral pressure to the first piece and the second piece folded into the cavity, and applying a vertical pressure to a first flange and a second flange of the first piece and the second piece, respectively, to form the composite blade stiffener.

FIELD

The present disclosure relates generally to methods for forming a flatcomposite charge into a composite blade stiffener, and moreparticularly, to forming the composite blade stiffener to a net form toenable application of barely visible impact damage treatments prior tocure.

BACKGROUND

Composite reinforcing substructures, such as blade stiffeners, sometimesreferred to as blade stringers, are commonly used in marine and aircraftindustries. These stringers may be fabricated by combining two or morestiffening members. For example, blade-type stringers can be fabricatedby combining two members having L or C cross sectional shapes,back-to-back. These members may be formed by manually hot drape formingmultiple composite charges over a mandrel or other tool. After forming,the members are placed back-to-back and co-cured in an autoclave.Fabricating blade stringers using multiple separate charges requiresmultiple tools, is relatively labor intensive and may add tomanufacturing flow times.

Structures formed from composite materials, such as blade stiffeners,are susceptible to subsurface damage following an impact. While asurface of a composite structure with low-energy/low-velocity impactdamage may show little or no visible signs of damage, such impacts maycause subsurface damage, such as delamination, which may be difficult todetect without sophisticated analysis. To protect for such non-visibledamage states, composite structures may be designed with impact witnesstreatments, which may lower the impact energy required to generatebarely visible impact damage (BVID), such that a correspondinggeneration of BVID will occur due to significant subsurface damage.

To allow for BVID detection, a treatment that may include glass fibersand a matrix material is applied to those composite structures that areat risk for impact damage, such as blade stiffeners on a wing skin panelof an aircraft. To apply this treatment, blade stiffeners generallyrequire post-cure trim operations at a top of a web and subsequent BVIDtreatment application involving surface preparation, vacuum bagging, andan additional cure cycle. These additional process steps increase a costof manufacturing this type of structure.

Accordingly, there is a need for a method for forming a compositestructure to enable co-cure BVID treatment to be applied directly afterforming the composite structure.

SUMMARY

In one example, a method for forming a flat composite charge into acomposite blade stiffener is described. The method comprises trimming aflat composite charge to a final design dimension, cutting the flatcomposite charge along a cut line into a first piece and a second pieceseparated by edges having an angle, applying a reinforcement ply overthe first piece and the second piece to hold the first piece and thesecond piece together, applying a ply of contact material to a formingmandrel, positioning the first piece and the second piece of the flatcomposite charge on the ply of contact material on the forming mandrelabout a tooling plunger such that the tooling plunger is aligned withthe cut line, activating the tooling plunger to contact thereinforcement ply and drive the first piece and the second piece of theflat composite charge into a cavity of the forming mandrel resulting inthe first piece and the second piece folding at the cut line,withdrawing the tooling plunger from the cavity of the forming mandrel,compressing the forming mandrel to apply a lateral pressure to the firstpiece and the second piece folded into the cavity, and applying avertical pressure to a first flange and a second flange of the firstpiece and the second piece, respectively, to form the composite bladestiffener.

In another example, a method is described comprising assembling a flatcomposite charge to a thickness in a predetermined orientation; forminga cut line on the flat composite charge having opposing 45 degreebeveled edges angled outward from the cut line, positioning the flatcomposite charge centered about a tooling plunger such that the toolingplunger is aligned with the cut line, and activating the tooling plungerto move downward and fold the flat composite charge at the cut line intoa cavity of a forming mandrel. At completion of movement of the toolingplunger and resulting folding of the flat composite charge, the opposed45 degree beveled edges form a flat surface perpendicular to the cutline and form a first flange and a second flange connected to the flatsurface.

In another example, another method for forming a flat composite chargeinto a composite blade stiffener is described. The method comprisescutting the flat composite charge along a cut line into two piecesseparated by edges having opposing 45 degree edges angled outward fromthe cut line, positioning the flat composite charge on a forming mandrelabout a tooling plunger such that the tooling plunger is aligned withthe cut line, activating the tooling plunger to drive the two pieces ofthe flat composite charge into a cavity of the forming mandrel resultingin the opposed 45 degree edges forming a flat surface perpendicular tothe cut line and a first flange and a second flange connected to theflat surface, withdrawing the tooling plunger from the cavity of theforming mandrel, compressing the forming mandrel to apply a lateralpressure to the two pieces folded into the cavity, applying a verticalpressure to the first flange and the second flange to form the compositeblade stiffener, applying a barely visible impact damage (BVID)treatment to the composite blade stiffener, and curing both thecomposite blade stiffener and the BVID treatment during a single curingprocess.

The features, functions, and advantages that have been discussed can beachieved independently in various examples or may be combined in yetother examples further details of which can be seen with reference tothe following description and drawings.

BRIEF DESCRIPTION OF THE FIGURES

The novel features believed characteristic of the illustrative examplesare set forth in the appended claims. The illustrative examples,however, as well as a preferred mode of use, further objectives anddescriptions thereof, will best be understood by reference to thefollowing detailed description of an illustrative examples of thepresent disclosure when read in conjunction with the accompanyingdrawings, wherein:

FIG. 1 illustrates an example flat composite charge, according to anexample.

FIG. 2 illustrates the flat composite charge trimmed to a final designdimension, according to an example.

FIG. 3 illustrates the flat composite charge modified to be formed intoa composite blade stiffener, according to an example.

FIG. 4 illustrates the flat composite charge positioned for formationinto the composite blade stiffener, according to an example.

FIG. 5 illustrates activation of the tooling plunger and formation ofthe flat composite charge into the composite blade stiffener, accordingto an example.

FIG. 6 illustrates completion of the tooling plunger motion and furtherformation of the flat composite charge into the composite bladestiffener, according to an example.

FIG. 7 illustrates removal of the tooling plunger, according to anexample.

FIG. 8 illustrates yet further formation of the flat composite chargeinto the composite blade stiffener, according to an example.

FIG. 9 shows another version of the formed composite blade stiffener,according to an example.

FIG. 10 illustrates an example of the composite blade stiffener,according to an example.

FIG. 11 illustrates another example formation of the flat compositecharge into the composite blade stiffener, according to an example.

FIG. 12 shows a flowchart of an example method for forming the flatcomposite charge into the composite blade stiffener, according to anexample.

FIG. 13 shows a flowchart of another example method, according to anexample.

FIG. 14 shows a flowchart of another example method for forming the flatcomposite charge into the composite blade stiffener, according to anexample.

DETAILED DESCRIPTION

Disclosed examples will now be described more fully hereinafter withreference to the accompanying drawings, in which some, but not all ofthe disclosed examples are shown. Indeed, several different examples maybe described and should not be construed as limited to the examples setforth herein. Rather, these examples are described so that thisdisclosure will be thorough and complete and will fully convey the scopeof the disclosure to those skilled in the art.

Example methods described herein relate to fabrication of compositestructures, such as processes for forming flat composite charges intoreinforcing substructures including blade-type stiffeners and stiffenersthat are contoured and/or have a variable gauge. Blade-type stiffenersmay be fabricated using a variety of different processes, and generallyrequire post-cure trim operations at a top of a web and subsequentbarely visible impact damage (BVID) treatment application involvingsurface preparation, vacuum bagging, and an additional cure cycle.Example methods described herein relate to forming a flat compositecharge into a final design geometry of a blade stiffener, and do notrequire subsequent processes such as green trim operations afterforming, post-cure web trim operations, and post-cure BVID treatmentapplication processes.

The blade stiffener is trimmed to final dimensions and edges are trimmedwith specific angles allowing post-formed geometry to match a finaldesign geometry. A reinforcement ply may be used to hold the chargetogether during the forming operation. A ply of contact material, suchas polyester peel ply, may be used to provide tensioning of the chargeduring the forming operation. The formed blade stiffener structureenables BVID treatment to be applied prior to cure, directly afterforming, thus reducing or eliminating multiple processes and relatedcost that generally would be required for this type of structure. Theblade stiffener with the applied BVID treatment can then be co-cured.Co-cure BVID treatment is estimated to save a large percentage of thepost cure BVID recurring cost, and will save floor space andnon-recurring costs as well.

Referring now to the figures, FIGS. 1-3 illustrate preparation of a flatcomposite charge 100 for formation into a final design geometry of acomposite blade stiffener, according to examples.

FIG. 1 illustrates the flat composite charge 100, according to anexample. The flat composite charge 100 includes multiple plies 102, 104,106, and 108 of composite material that are stacked on top of eachother. Example composite material that may be used includes alightweight material, such as an uncured pre-impregnated reinforcingtape or fabric (i.e., “prepreg”). The tape or fabric can include aplurality of fibers such as graphite fibers that are embedded within amatrix material, such as a polymer, e.g., an epoxy or phenolic. The tapeor fabric could be unidirectional or woven depending on a degree ofreinforcement desired. The plies 102, 104, 106, and 108 could be anysuitable dimension to provide various degrees of reinforcement, and theflat composite charge 100 could comprise any number of plies of prepregtape or fabric.

The plies 102, 104, 106, and 108 are laid on top of each other, andlined up to a predetermined dimension and/or predetermined orientation.A number of plies to be stacked may depend on a final design geometry ofthe flat composite charge 100, and thus, the flat composite charge 100can be assembled to have a desired thickness in a predeterminedorientation. The flat composite charge 100 is then trimmed to a finaldesign dimension.

FIG. 2 illustrates the flat composite charge 100 trimmed to a finaldesign dimension, according to an example. The flat composite charge 100includes trimmed ends 110 and 112, which are trimmed at an angle to forman angled edge.

Next, to enable the flat composite charge 100 to be formed into acomposite blade stiffener, further modifications to the flat compositecharge 100 are made as shown in FIG. 3. FIG. 3 illustrates the flatcomposite charge cut along a cut line 114 into a first piece 116 and asecond piece 118, or into two pieces, according to an example. In theexample shown in FIG. 3, the cut line 114 is an approximate centerlineof the flat composite charge 100. In other examples, the cut line 114 isoff center for other final design geometries of the composite bladestiffener.

The flat composite charge 100 is cut while laid flat so as to be formedinto a net profile desired for a final design geometry to reduceprocessing costs related to any additional post-processing that wouldotherwise be required.

The first piece 116 and the second piece 118 are separated by edges 120and 122 having an angle. In the example shown in FIG. 3, the angle is 45degrees, or may be about 45 degrees. In other examples, the angle may beless than or greater than 45 degrees, such as in a range of about 30degrees to about 80 degrees. In still further examples, the angle can bein a range that is less than 90 degrees and greater than 0 degrees basedon a final design geometry of the composite blade stiffener.

By the terms “substantially” or “about” used herein, it is meant thatthe recited characteristic, parameter, or value need not be achievedexactly, but that deviations or variations, including for example,tolerances, measurement error, measurement accuracy limitations andother factors known to skill in the art, may occur in amounts that donot preclude the effect the characteristic was intended to provide.

In FIG. 3, the edges 120 and 122 are shown as opposing 45 degree edgesangled outward from the cut line 114. The edges 120 and 122 may beconsidered beveled edges in some examples.

Once the flat composite charge 100 is prepared, the flat compositecharge 100 can be positioned onto a forming mandrel for formation intothe composite blade stiffener.

FIG. 4 illustrates the flat composite charge 100 positioned forformation into the composite blade stiffener, according to an example.Initially, a reinforcement ply 124 is applied over the first piece 116and the second piece 118 (e.g., the two pieces) to hold the first piece116 and the second piece 118 together after being cut. For example, thereinforcement ply 124 is applied over the flat composite charge 100. Inan example, the reinforcement ply 124 is a composite fabric ply.

A forming mandrel including a first block 126 and a second block 128 areused, and a ply of contact material 130 is applied to the first block126 and the second block 128 of the forming mandrel. In an example, theply of contact material 130 is a polyester peel ply. In furtherexamples, more than one layer of ply or more than one ply may be used.

The flat composite charge 100 including the first piece 116 and thesecond piece 118 is then positioned on the ply of contact material 130on the first block 126 and the second block 128 of the forming mandrelabout a tooling plunger 132 such that the tooling plunger 132 is alignedwith the cut line 114 or centered in relation to the angled edges. Inone example, the flat composite charge 100 is centered about the toolingplunger 132. In other examples, the flat composite charge 100 is offcenter for other final design geometries of the composite bladestiffener. The tooling plunger 132 may then be activated.

FIG. 5 illustrates activation of the tooling plunger 132, according toan example. The tooling plunger 132 is activated to contact thereinforcement ply 124 and drive the first piece 116 and the second piece118 of the flat composite charge 100 into a cavity 134 of the firstblock 126 and the second block 128 of the forming mandrel resulting inthe first piece 116 and the second piece 118 folding at the cut line 114about the tooling plunger 132. In one example, the first block 126 andthe second block 128 of the forming mandrel are separated as the toolingplunger 132 moves downward, as shown in FIG. 5. The reinforcement ply124 will help to hold the first piece 116 and the second piece 118together during punch down of the tooling plunger 132.

Within examples, the flat composite charge 100 is heated prior toactivating the tooling plunger 132. In one example, the flat compositecharge is heated to about 130 degrees F. To drive the tooling plunger132 downward and cause the first piece 116 and the second piece 118 ofthe flat composite charge 100 into the cavity, a force of less than 100lbs per foot may be applied, and in some examples, the activation of thetooling plunger 132 occurs in less than about 5 minutes after heatingthe flat composite charge.

FIG. 6 illustrates completion of the tooling plunger motion and furtherformation of the flat composite charge 100 into the composite bladestiffener, according to an example.

FIG. 7 illustrates removal of the tooling plunger 132. After activationof the tooling plunger 132, the tooling plunger 132 can be withdrawnfrom the cavity 134 of the forming mandrel. To withdraw the toolingplunger 132, the tooling plunger is lifted out of the cavity 134. Insome examples, a plate 140 is loaded over a first flange 136 and asecond flange 138 of the first piece and the second piece 118,respectively, following withdrawal and removal of the tooling plunger132 from the cavity 134 of the forming mandrel, and a vertical pressureis applied to the first flange 136 and the second flange 138 using theplate 140. The vertical pressure may be less than 1 psi in thisinstance, for example.

FIG. 8 illustrates yet further formation of the flat composite charge100 into the composite blade stiffener as the first block 126 and thesecond block 128 of the forming mandrel are compressed to apply alateral pressure to a portion of the first piece 116 and to a portion ofthe second piece 118 folded into the cavity 134. The lateral pressuremay be applied by air hoses (not shown) pushing the first block 126 andthe second block 128 toward each other. In addition, followingapplication of lateral pressure, a greater vertical pressure is appliedto the first flange 136 and the second flange 138 of the first piece 116and the second piece 118, respectively, to form the composite bladestiffener.

FIG. 9 illustrates yet further formation of the flat composite charge100 into the composite blade stiffener, according to an example. Afiller 144 can be applied between the first flange 136 and the secondflange 138, and additional plies 142 can be stacked on top of the firstflange 136 and the second flange 138. To do so, the plate 140 is lifted,and the additional materials are added. Following, additional verticaland lateral pressure can then be applied as well.

FIG. 10 illustrates an example of the composite blade stiffener 146,according to an example. At completion of movement of the toolingplunger 132 and resulting folding of the flat composite charge 100, theopposed 45 degree edges 120 and 122 form a flat surface 148 alignedwith, perpendicular to, or along the cut line 114 and form a web 152 andthe first flange 136 and the second flange 138 are connected to the flatsurface 148. Thus, the flat surface 148, the first flange 136 and thesecond flange 138, and the web 152 connected to the flat surface 148,form the composite blade stiffener 146. Within an example, applying thevertical pressure to the first flange 136 and the second flange 138 ofthe first piece 116 and the second piece 118, respectively, to form thecomposite blade stiffener 146 includes applying the vertical pressure toform a T-shaped structure with a substantially flat top in relation tothe web 152, as shown in FIG. 8. The initial 45 degree cut angle enablesformation of the composite blade stiffener 146 in the final designgeometry having the flat surface 148 perpendicular to the web 152.

In some examples, a barely visible impact damage (BVID) treatment 150 isthen applied to the composite blade stiffener 146. The BVID treatment150 is provided to enable impact damage to the composite blade stiffener146 to be visible. For example, during fabrication or in-service, impactto the composite blade stiffener 146 can cause internal or non-visibledamage since damage to composite materials is often difficult tovisualize. The BVID treatment 150, however, will show damage above acertain energy/velocity threshold (to avoid false positive indications).In an example, the BVID treatment 150 may include a fiberglass overwrapor clear resin material, which acts as a witness strip, such that whenimpacted, the fiberglass will be physically altered and impact damagecan be visually determined. Thus, the fiberglass overwrap can be used toidentify imperfections in the composite blade stiffener 146 due toimpact.

The BVID treatment 150 can be applied to the flat surface 148 and theweb 152, as shown in FIG. 10. After application of the BVID treatment150, both the composite blade stiffener 146 and the BVID treatment 150can be cured during a single curing process.

FIG. 11 illustrates another example formation of the flat compositecharge 100 into the composite blade stiffener 146, according to anexample. In FIG. 11, the BVID treatment 150 is shown to be applied to abottom surface of the first piece 116 and the second piece 118 of theflat composite charge 100 prior to activation of the tooling plunger 132and formation of the composite blade stiffener 146. Thus, the BVIDtreatment 150 can be applied before or after formation of the compositeblade stiffener 146. In either example, both the composite bladestiffener 146 and the BVID treatment 150 can be cured during a singlecuring process to save time and money.

FIG. 12 shows a flowchart of an example method 200 for forming the flatcomposite charge 100 into the composite blade stiffener 146, accordingto an example. Method 200 shown in FIG. 12 presents an example of amethod that could be used during formation of the composite bladestiffener 146 as shown in FIGS. 4-11, for example. Further, devices orsystems may be used or configured to perform logical functions presentedin FIG. 12. In some instances, components of the devices and/or systemsmay be configured to perform the functions such that the components areactually configured and structured (with hardware and/or software) toenable such performance. In other examples, components of the devicesand/or systems may be arranged to be adapted to, capable of, or suitedfor performing the functions, such as when operated in a specificmanner. Method 200 may include one or more operations, functions, oractions as illustrated by one or more of blocks 202-218. Also, thevarious blocks may be combined into fewer blocks, divided intoadditional blocks, and/or removed based upon the desired implementation.

It should be understood that for this and other processes and methodsdisclosed herein, flowcharts show functionality and operation of onepossible implementation of present examples. Alternative implementationsare included within the scope of the examples of the present disclosurein which functions may be executed out of order from that shown ordiscussed, including substantially concurrent or in reverse order,depending on the functionality involved, as would be understood by thosereasonably skilled in the art.

At block 202, the method 200 includes trimming the flat composite charge100 to a final design dimension. The final design dimension may includea specified thickness as well as specified length of the flat compositecharge 100, for example.

At block 204, the method 200 includes cutting the flat composite charge100 along the cut line 114 into the first piece 116 and the second piece118 separated by the edges 120 and 122 having an angle. In an example,cutting the flat composite charge 100 along the cut line 114 includescutting the flat composite charge 100 along a centerline. In furtherexamples, the cutting results in the edges 120 and 122 having about a 45degree angle, and the edges 120 and 122 may be angled outward from thecut line 114.

At block 206, the method 200 includes applying the reinforcement ply 124over the first piece 116 and the second piece 118 to hold the firstpiece 116 and the second piece 118 together. The reinforcement ply 124may include a composite fabric ply.

At block 208, the method 200 includes applying the ply of contactmaterial 130 to a forming mandrel. The ply of contact material 130 mayinclude a polyester peel ply.

At block 210, the method 200 includes positioning the first piece 116and the second piece 118 of the flat composite charge 100 on the ply ofcontact material 130 on the forming mandrel about the tooling plunger132 such that the tooling plunger 132 is aligned with or perpendicularto the cut line 114. In some examples, the first piece 116 and thesecond piece 118 are positioned to be centered in relation to the edgeshaving an angle.

At block 212, the method 200 includes activating the tooling plunger 132to contact the reinforcement ply 124 and drive the first piece 116 andthe second piece 118 of the flat composite charge 100 into the cavity134 of the forming mandrel resulting in the first piece 116 and thesecond piece 118 folding at the cut line 114. The first piece 116 andthe second piece may also fold about the tooling plunger 132. In someexamples, the flat composite charge 100 is heated prior to activatingthe tooling plunger 132.

At block 214, the method 200 includes withdrawing the tooling plunger132 from the cavity 134 of the forming mandrel. In one example, thetooling plunger 132 may be removed from the forming mandrel as well.

At block 216, the method 200 includes compressing the forming mandrel toapply a lateral pressure to the first piece 116 and the second piece 118folded into the cavity 134. The lateral pressure forms the first piece116 and the second piece 118 into a substantially flat section, forexample.

At block 218, the method 200 includes applying a vertical pressure tothe first flange 136 and the second flange 138 of the first piece 116and the second piece 118, respectively, to form the composite bladestiffener 146. Applying the vertical pressure forms a T-shaped structurewith a substantially flat top in relation to the web 152, for example.

Within examples, the method 200 may additionally include loading theplate 140 over the first flange 136 and the second flange 138 followingwithdrawal of the tooling plunger 132 from the cavity 134 of the formingmandrel, and applying the vertical pressure to the first flange 136 andthe second flange 138 using the plate 140.

Within additional examples, the method 200 may also include applying theBVID 150 treatment to the composite blade stiffener 146, and curing boththe composite blade stiffener 146 and the BVID treatment 150 during asingle curing process.

FIG. 13 shows a flowchart of an example method 220, according to anexample. Method 220 shown in FIG. 13 presents an example of a methodthat could be used during formation of the composite blade stiffener 146as shown in FIGS. 4-11, for example. Further, devices or systems may beused or configured to perform logical functions presented in FIG. 13. Insome instances, components of the devices and/or systems may beconfigured to perform the functions such that the components areactually configured and structured (with hardware and/or software) toenable such performance. In other examples, components of the devicesand/or systems may be arranged to be adapted to, capable of, or suitedfor performing the functions, such as when operated in a specificmanner. Method 220 may include one or more operations, functions, oractions as illustrated by one or more of blocks 222-228. Also, thevarious blocks may be combined into fewer blocks, divided intoadditional blocks, and/or removed based upon the desired implementation.

At block 222, the method 220 includes assembling the flat compositecharge 100 to a thickness in a predetermined orientation. At block 224,the method 220 includes forming the cut line 114 on the flat compositecharge 100 having opposing 45 degree beveled edges 120 and 122 angledoutward from the cut line 114. At block 226, the method 220 includespositioning the flat composite charge 100 centered about the toolingplunger 132 such that the tooling plunger 132 is aligned with the cutline 114.

At block 228, the method 220 includes activating the tooling plunger 132to move downward and fold the flat composite charge 100 at the cut line114 into the cavity 134 of a forming mandrel, and at completion ofmovement of the tooling plunger 132 and resulting folding of the flatcomposite charge 100, the opposed 45 degree beveled edges 120 and 122form the flat surface 148 aligned with, or perpendicular to the cut line114 and form the first flange 136 and the second flange 138 connected tothe flat surface 148. In examples, at completion, the web 152 is alsoformed connected to the flat surface 148. In some examples, the flatcomposite charge 100 is heated prior to activating the tooling plunger132, and the forming mandrel is separated as the tooling plunger 132moves downward.

Within examples, the method 220 may additionally include applying thereinforcement ply 124 over the flat composite charge 100 prior toactivation of the tooling plunger 132.

Within other examples, the method 220 may additionally include loadingthe plate 140 over the first flange 136 and the second flange 138following withdrawal of the tooling plunger 132 from the cavity 134 ofthe forming mandrel, and applying a vertical pressure to the firstflange 136 and the second flange 138 using the plate 140.

Within still other examples, the flat surface 148, and the first flange136 and the second flange 138 and the web 152 connected to the flatsurface 148, form the composite blade stiffener 146, and the method 220may additionally include applying the BVID treatment 150 to thecomposite blade stiffener 146, and curing both the composite bladestiffener 146 and the BVID treatment 150 during a single curing process.

FIG. 14 shows a flowchart of another example method 230 for forming theflat composite charge 100 into the composite blade stiffener 146,according to an example. Method 230 shown in FIG. 14 presents an exampleof a method that could be used during formation of the composite bladestiffener 146 as shown in FIGS. 4-11, for example. Further, devices orsystems may be used or configured to perform logical functions presentedin FIG. 14. In some instances, components of the devices and/or systemsmay be configured to perform the functions such that the components areactually configured and structured (with hardware and/or software) toenable such performance. In other examples, components of the devicesand/or systems may be arranged to be adapted to, capable of, or suitedfor performing the functions, such as when operated in a specificmanner. Method 230 may include one or more operations, functions, oractions as illustrated by one or more of blocks 232-246. Also, thevarious blocks may be combined into fewer blocks, divided intoadditional blocks, and/or removed based upon the desired implementation.

At block 232, the method 230 includes cutting the flat composite charge100 along the cut line 114 into two pieces 116 and 118 separated byedges 120 and 122 having opposing 45 degree edges angled outward fromthe cut line 114. At block 234, the method 230 includes positioning theflat composite charge 100 on a forming mandrel about the tooling plunger132 such that the tooling plunger 132 is aligned with the cut line 114or centered in relation to the 45 degree edges. At block 236, the method230 includes activating the tooling plunger 132 to drive the two pieces116 and 118 of the flat composite charge 100 into the cavity 134 of theforming mandrel resulting in the opposed 45 degree edges 120 and 122forming the flat surface 148 along the cut line 114 and the first flange136 and the second flange 138 connected to the flat surface 148. Atblock 238, the method 230 includes withdrawing the tooling plunger 132from the cavity 134 of the forming mandrel. At block 240, the method 230includes compressing the forming mandrel to apply a lateral pressure tothe two pieces 116 and 118 folded into the cavity 134. At block 242, themethod 230 includes applying a vertical pressure to the first flange 136and the second flange 138 to form the composite blade stiffener 146. Atblock 244, the method 230 includes applying the BVID treatment 150 tothe composite blade stiffener 146. At block 246, the method 230 includescuring both the composite blade stiffener 146 and the BVID treatment 150during a single curing process.

Within examples, the method 230 may additionally include applying thereinforcement ply 124 over the two pieces 116 and 118 to hold the twopieces 116 and 118 together.

Within other examples, the method 230 may additionally include applyingthe ply of contact material 130 to the forming mandrel, and positioningthe flat composite charge 100 on the ply of contact material 130 on theforming mandrel.

Within still other examples, the method 230 may additionally includeloading the plate 140 over the first flange 136 and the second flange138 following withdrawal of the tooling plunger 132 from the cavity 134of the forming mandrel, and applying the vertical pressure to the firstflange 136 and the second flange 138 using the plate 140.

Using examples described herein, additional post-processing of thecomposite blade stiffener 146 can be reduced or eliminated since theflat composite charge 100 is prepared to enable formation of thecomposite blade stiffener 146 into the final net profile with noadditional trimming required. Further, this enables application of theBVID treatment 150 and curing of the composite blade stiffener 146 andthe BVID treatment 150 at the same time during a single cure process.

The description of the different advantageous arrangements has beenpresented for purposes of illustration and description, and is notintended to be exhaustive or limited to the examples in the formdisclosed. Many modifications and variations will be apparent to thoseof ordinary skill in the art. Further, different advantageous examplesmay describe different advantages as compared to other advantageousexamples. The example or examples selected are chosen and described inorder to best explain the principles of the examples, the practicalapplication, and to enable others of ordinary skill in the art tounderstand the disclosure for various examples with variousmodifications as are suited to the particular use contemplated.

What is claimed is:
 1. A method for forming a flat composite charge intoa composite blade stiffener, comprising: trimming a flat compositecharge to a final design dimension; cutting the flat composite chargealong a cut line into a first piece and a second piece separated byedges having an angle; applying a reinforcement ply over the first pieceand the second piece to hold the first piece and the second piecetogether; applying a ply of contact material to a forming mandrel;positioning the first piece and the second piece of the flat compositecharge on the ply of contact material on the forming mandrel about atooling plunger such that the tooling plunger is aligned with the cutline; activating the tooling plunger to contact the reinforcement plyand drive the first piece and the second piece of the flat compositecharge into a cavity of the forming mandrel resulting in the first pieceand the second piece folding at the cut line; withdrawing the toolingplunger from the cavity of the forming mandrel; compressing the formingmandrel to apply a lateral pressure to the first piece and the secondpiece folded into the cavity; and applying a vertical pressure to afirst flange and a second flange of the first piece and the secondpiece, respectively, to form the composite blade stiffener.
 2. Themethod of claim 1, wherein cutting the flat composite charge along thecut line comprises cutting the flat composite charge along a centerline.3. The method of claim 1, wherein cutting the flat composite chargealong the cut line into the first piece and the second piece separatedby the edges having the angle comprises cutting the edges to have abouta 45 degree angle.
 4. The method of claim 1, wherein cutting the flatcomposite charge along the cut line into the first piece and the secondpiece separated by the edges having the angle comprises cutting theedges to have opposing 45 degree edges angled outward from the cut line.5. The method of claim 1, wherein applying the reinforcement ply overthe first piece and the second piece to hold the first piece and thesecond piece together comprises applying a composite fabric ply.
 6. Themethod of claim 1, wherein applying the ply of contact material to theforming mandrel comprises applying a polyester peel ply.
 7. The methodof claim 1, wherein applying the vertical pressure to the first flangeand the second flange of the first piece and the second piece,respectively, to form the composite blade stiffener comprises applyingthe vertical pressure to form a T-shaped structure with a substantiallyflat top.
 8. The method of claim 1, further comprising: loading a plateover the first flange and the second flange following withdrawal of thetooling plunger from the cavity of the forming mandrel; and applying thevertical pressure to the first flange and the second flange using theplate.
 9. The method of claim 1, further comprising: applying a barelyvisible impact damage (BVID) treatment to the composite blade stiffener;and curing both the composite blade stiffener and the BVID treatmentduring a single curing process.
 10. The method of claim 1, furthercomprising: heating the flat composite charge prior to activating thetooling plunger.
 11. A method comprising: assembling a flat compositecharge to a thickness in a predetermined orientation; forming a cut lineon the flat composite charge having opposing 45 degree beveled edgesangled outward from the cut line; positioning the flat composite chargecentered about a tooling plunger such that the tooling plunger isaligned with the cut line; and activating the tooling plunger to movedownward and fold the flat composite charge at the cut line into acavity of a forming mandrel, wherein at completion of movement of thetooling plunger and resulting folding of the flat composite charge, theopposing 45 degree beveled edges form a flat surface perpendicular tothe cut line and form a first flange and a second flange connected tothe flat surface.
 12. The method of claim 11, further comprising:separating the forming mandrel as the tooling plunger moves downward.13. The method of claim 11, further comprising: applying a reinforcementply over the flat composite charge.
 14. The method of claim 11, furthercomprising: loading a plate over the first flange and the second flangefollowing withdrawal of the tooling plunger from the cavity of theforming mandrel; and applying a vertical pressure to the first flangeand the second flange using the plate.
 15. The method of claim 11,wherein the flat surface and the first flange and the second flangeconnected to the flat surface form a composite blade stiffener, and themethod further comprises: applying a barely visible impact damage (BVID)treatment to the composite blade stiffener; and curing both thecomposite blade stiffener and the BVID treatment during a single curingprocess.
 16. The method of claim 11, further comprising: heating theflat composite charge prior to activating the tooling plunger.
 17. Amethod for forming a flat composite charge into a composite bladestiffener, comprising: cutting the flat composite charge along a cutline into two pieces separated by edges having opposing 45 degree edgesangled outward from the cut line; positioning the flat composite chargeon a forming mandrel about a tooling plunger such that the toolingplunger is aligned with the cut line; activating the tooling plunger todrive the two pieces of the flat composite charge into a cavity of theforming mandrel resulting in the opposing 45 degree edges forming a flatsurface perpendicular to the cut line and a first flange and a secondflange connected to the flat surface; withdrawing the tooling plungerfrom the cavity of the forming mandrel; compressing the forming mandrelto apply a lateral pressure to the two pieces folded into the cavity;applying a vertical pressure to the first flange and the second flangeto form the composite blade stiffener; applying a barely visible impactdamage (BVID) treatment to the composite blade stiffener; and curingboth the composite blade stiffener and the BVID treatment during asingle curing process.
 18. The method of claim 17, further comprising:applying a reinforcement ply over the two pieces to hold the two piecestogether.
 19. The method of claim 17, further comprising: applying a plyof contact material to the forming mandrel; and positioning the flatcomposite charge on the ply of contact material on the forming mandrel.20. The method of claim 17, further comprising: loading a plate over thefirst flange and the second flange following withdrawal of the toolingplunger from the cavity of the forming mandrel; and applying thevertical pressure to the first flange and the second flange using theplate.